公开(公告)号：US10174946B2

公开(公告)日：2019-01-08

申请号：US14950876

申请日：2015-11-24

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka

IPC: F02C1/00 ,  F23R3/00 ,  F23R3/28

Abstract: A nozzle guide is provided for a combustor of a gas turbine engine. The nozzle guide includes an annular structure including a plurality of cooling holes, a guide plate including a plurality of openings on an outer periphery of the guide plate, and a plurality of cooling passages within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings.

公开(公告)号：US20170009987A1

公开(公告)日：2017-01-12

申请号：US15113536

申请日：2015-02-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Randal G. McKinney ,  Frank J. Cunha ,  Stanislav Kostka, JR.

IPC: F23R3/00 ,  F02C7/24 ,  F23R3/06

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.

Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括具有外壳和隔热罩的燃烧器壁。 燃烧器壁限定了通过其的淬火孔。 燃烧器壁还在外壳和隔热罩之间限定一个空腔。 壳体限定空气被引导到空腔中的第一孔。 隔热罩包括至少部分地限定第二孔的导轨，该第二孔构造成将空腔内的至少一些空气引导出燃烧器壁并且朝向骤冷孔。

公开(公告)号：US20160265775A1

公开(公告)日：2016-09-15

申请号：US15034717

申请日：2014-11-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha ,  Stanislav Kostka, JR.

IPC: F23R3/00 ,  F23R3/50 ,  F23R3/06

Abstract: A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.

Abstract translation: 提供了一种用于涡轮发动机的结构。 该结构包括具有第一表面的外壳和具有带纹理的第二表面和纹理的第三表面的隔热罩。 第二表面的一部分的纹理不同于第三表面的一部分的质地。 第一表面和第二表面限定了壳体和隔热罩之间的第一冷却腔。 第一表面和第三表面在外壳和隔热罩之间限定第二冷却腔。

公开(公告)号：US20160230662A1

公开(公告)日：2016-08-11

申请号：US14618298

申请日：2015-02-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Stanislav Kostka, JR. ,  Frank J. Cunha

IPC: F02C7/18 ,  F23R3/00

CPC classification number: F02C7/18 ,  F01D5/187 ,  F01D25/08 ,  F05D2260/2212 ,  F05D2260/22141 ,  F23R3/005

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling scheme disposed inside the body portion, the cooling scheme including a vascular engineered lattice structure and a heat transfer device adjacent to the vascular engineered lattice structure.

Abstract translation: 根据本公开的示例性方面的部件包括布置在主体部分内部的主体部分和冷却方案，所述冷却方案包括血管工程格子结构和邻近血管工程格子的传热装置 结构体。

公开(公告)号：US20160201909A1

公开(公告)日：2016-07-14

申请号：US14910964

申请日：2014-08-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James P. Bangerter ,  Kevin J. Low ,  Russell B. Hanson ,  Nurhak Erbas-Sen ,  Frank J. Cunha

IPC: F23R3/00 ,  F23R3/60 ,  F23R3/06

Abstract: A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.

Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器的壁组件。 壁组件包括具有轮廓区域的支撑壳体，以在支撑壳体和多个衬板之间限定至少一个会聚通道。 还提供了一种冷却燃气涡轮发动机的燃烧器的壁组件的方法。 该方法包括将冷却空气引导到支撑壳和多个衬板之间的至少一个会聚通道的步骤。

公开(公告)号：US20160146465A1

公开(公告)日：2016-05-26

申请号：US14950876

申请日：2015-11-24

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka

IPC: F23R3/10 ,  F23R3/00

CPC classification number: F23R3/002 ,  F23R3/283 ,  F23R2900/03043 ,  F23R2900/03044

Abstract: A nozzle guide is provided for a combustor of a gas turbine engine. The nozzle guide includes an annular structure including a plurality of cooling holes, a guide plate including a plurality of openings on an outer periphery of the guide plate, and a plurality of cooling passages within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings.

Abstract translation: 为燃气轮机的燃烧器提供喷嘴引导件。 所述喷嘴引导件包括环形结构，所述环形结构包括多个冷却孔，在所述导向板的外周上包括多个开口的引导板，以及在所述环形结构内的多个冷却通道，以提供来自所述多个冷却 孔到多个开口。

公开(公告)号：US20150369490A1

公开(公告)日：2015-12-24

申请号：US14765227

申请日：2014-02-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha ,  Nurhak Erbas-Sen

IPC: F23R3/50 ,  F23R3/00

CPC classification number: F23R3/50 ,  F23R3/002 ,  F23R3/60 ,  F23R2900/03042 ,  Y02T50/675 ,  Y10T29/49828

Abstract: A heat shield for a combustor of a gas turbine engine includes a first edge with a first set of cantilevered members and a second edge with a second set of cantilevered members.

Abstract translation: 用于燃气涡轮发动机的燃烧器的隔热罩包括具有第一组悬臂构件的第一边缘和具有第二组悬臂构件的第二边缘。

公开(公告)号：US20140216044A1

公开(公告)日：2014-08-07

申请号：US13716774

申请日：2012-12-17

Applicant: United Technologies Corporation

Inventor： Nurhak Erbas-Sen ,  James B. Hoke ,  Frank J. Cunha

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/675

Abstract: A heat shield for a gas turbine engine includes a hot side with one or more raised features that extend therefrom.

Abstract translation: 用于燃气涡轮发动机的隔热罩包括具有从其延伸的一个或多个凸起特征的热侧。

公开(公告)号：US10935244B2

公开(公告)日：2021-03-02

申请号：US16167873

申请日：2018-10-23

Applicant: United Technologies Corporation

Inventor： Stanislav Kostka ,  Frank J. Cunha

IPC: F23R3/00 ,  F23M5/00 ,  F23R3/06 ,  F23M5/08 ,  F23R3/08 ,  F23M5/04 ,  F23R3/60

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.

公开(公告)号：US10386066B2

公开(公告)日：2019-08-20

申请号：US15032190

申请日：2014-11-21

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr.

IPC: F23R3/00 ,  F23M5/08 ,  F23R3/06 ,  F02C7/18 ,  F02C7/24 ,  F23R3/44

Abstract: A multi-walled structure is provided for a turbine engine. This structure includes a shell with a textured first surface, and a heat shield with a second surface. The heat shield is attached to the shell. The first and the second surfaces vertically define a cooling cavity between the shell and the heat shield. The cooling cavity fluidly couples a plurality of cooling apertures defined in the shell with a plurality of cooling apertures defined in the heat shield.